Adaptive Sliding Mode Control for Spacecraft Rendezvous in Near-Circular Orbits with Time-Varying Saturation Constraint

被引：0

作者：

Wan, Neng ^{[1
]}

Naidu, D. Subbaram ^{[2
]}

Liu, Ming ^{[3
]}

Wu, Ligang ^{[4
]}

Yao, Weiran ^{[5
]}

机构：

[1] Univ Minnesota Duluth, Dept Math & Stat, Duluth, MN 55812 USA

[2] Univ Minnesota Duluth, Dept Elect Engn, Duluth, MN 55812 USA

[3] Harbin Inst Technol, Res Ctr Satellite Technol, Harbin 150080, Heilongjiang, Peoples R China

[4] Harbin Inst Technol, Res Inst Intelligent Control & Syst, Harbin 150001, Heilongjiang, Peoples R China

[5] Harbin Inst Technol, Sch Astronaut, Harbin 150001, Heilongjiang, Peoples R China

来源：

2017 AMERICAN CONTROL CONFERENCE (ACC) | 2017年

基金：

中国国家自然科学基金;

关键词：

OUTPUT-FEEDBACK CONTROL; ACTUATOR SATURATION; ROBUST; SYSTEMS;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

An adaptive sliding mode control scheme is proposed for spacecraft rendezvous constrained by the external perturbations, the non-circularity of reference orbit, and the time-varying saturation, which can be induced by the temporal characteristics and the accidental faults of actuators. With some reasonable assumptions, we prove that the adaptive control scheme can achieve asymptotic stability without using the effectiveness information of actuators. Compared with the existing results, numerical experiment with longer initial distances, lower saturation bounds, and better performance is achieved within a nonlinear two-body system.

引用

页码：5812 / 5817

页数：6

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